By John J. Bertin
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Additional resources for Aerodynamics for Engineers,
12) for example]. Finally, the units of the equation are force per unit volume, since we divided through by the volume during the derivation. For a general application, the unknown parameters that appear in the NavierStokes equations are the three velocity components (u, v, and w), the pressure (p), the density (r), and the viscosity (m). 12), respectively]. Therefore, we have five primary (or primitive) variables for a general flow problem: the three velocity components, the pressure, and the temperature.
The lift-to-drag ratio is, therefore, a maximum 3(L>D)max 4. What is the maximum value of the lift-to-drag ratio 3(L>D)max 4 for our 5,000-lbf T-38A cruising at 26,000 ft? What is the velocity at which the vehicle cruises, when the lift-to-drag ratio is a maximum? As the vehicle slows to speeds below that for 3(L>D)min 4, which is equal to 3(L>D)max 4, it actually requires more thrust (i. , more power) to fly slower. You are operating the aircraft in the region of reverse command. More thrust is required to cruise at a slower speed.
This tells us that Sec. 4 / Applications to Constant-Property Flows 59 h 2 h at y = + 2 at y = - u = 0 u = 0 When we apply these conditions, we find that: C1 = 0 C2 = - 1 dp h2 2m dx 4 which results in a velocity profile given by: u = + 1 dp 2 h2 ay b 2m dx 4 The velocity profile is parabolic, with the maximum velocity occurring at the center of the channel, as shown in Fig. 8. The shear stress distribution is given by: t = m dp du 1 dp = 2m y = y dy 2m dx dx The lower wall is given by y = -h>2 and the upper wall is given by y = +h>2.
Aerodynamics for Engineers, by John J. Bertin